Hybrid approach in the initial aerodynamic, stability and performance calculations of a light airplane
Апстракт
The paper is focused on the preliminary aerodynamic analyses of a new light aircraft in symmetrical flight configurations. Initial calculations have been done using a 3D vortex lattice method. Since this method is based on inviscid flow concept, the non-linear calibration diagrams for the effectiveness and circulation of control surfaces have been derived from wind tunnel test data of an existing airplane. These calibration functions have been interpolated for a new light aircraft geometry, and analyses of lift and moment coefficients with different flaps and elevator deflections have been performed. Deflected flaps and elevator generate local lift redistributions which contribute to the induced drag, even at angles of attack when the total airplane lift is zero, which has been successfully determined by the applied CFD model. Parasite drag components, omitted by CFD calculations, have been obtained using DVL and Datcom methods and superimposed with CFD results, giving complete new air...craft polars, which have been successfully applied in longitudinal stability and basic performance estimates.
Кључне речи:
symmetrical flight conditions / stability and performance / light aircraft / hybrid method / aerodynamicsИзвор:
Tehnički vjesnik, 2013, 20, 4, 605-614Издавач:
- Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek
Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Kostić, Ivan AU - Stefanović, Zoran AU - Petrović, Zlatko AU - Kostić, Olivera AU - Essari, Abdulhakim PY - 2013 UR - https://machinery.mas.bg.ac.rs/handle/123456789/1796 AB - The paper is focused on the preliminary aerodynamic analyses of a new light aircraft in symmetrical flight configurations. Initial calculations have been done using a 3D vortex lattice method. Since this method is based on inviscid flow concept, the non-linear calibration diagrams for the effectiveness and circulation of control surfaces have been derived from wind tunnel test data of an existing airplane. These calibration functions have been interpolated for a new light aircraft geometry, and analyses of lift and moment coefficients with different flaps and elevator deflections have been performed. Deflected flaps and elevator generate local lift redistributions which contribute to the induced drag, even at angles of attack when the total airplane lift is zero, which has been successfully determined by the applied CFD model. Parasite drag components, omitted by CFD calculations, have been obtained using DVL and Datcom methods and superimposed with CFD results, giving complete new aircraft polars, which have been successfully applied in longitudinal stability and basic performance estimates. PB - Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek T2 - Tehnički vjesnik T1 - Hybrid approach in the initial aerodynamic, stability and performance calculations of a light airplane EP - 614 IS - 4 SP - 605 VL - 20 UR - https://hdl.handle.net/21.15107/rcub_machinery_1796 ER -
@article{ author = "Kostić, Ivan and Stefanović, Zoran and Petrović, Zlatko and Kostić, Olivera and Essari, Abdulhakim", year = "2013", abstract = "The paper is focused on the preliminary aerodynamic analyses of a new light aircraft in symmetrical flight configurations. Initial calculations have been done using a 3D vortex lattice method. Since this method is based on inviscid flow concept, the non-linear calibration diagrams for the effectiveness and circulation of control surfaces have been derived from wind tunnel test data of an existing airplane. These calibration functions have been interpolated for a new light aircraft geometry, and analyses of lift and moment coefficients with different flaps and elevator deflections have been performed. Deflected flaps and elevator generate local lift redistributions which contribute to the induced drag, even at angles of attack when the total airplane lift is zero, which has been successfully determined by the applied CFD model. Parasite drag components, omitted by CFD calculations, have been obtained using DVL and Datcom methods and superimposed with CFD results, giving complete new aircraft polars, which have been successfully applied in longitudinal stability and basic performance estimates.", publisher = "Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek", journal = "Tehnički vjesnik", title = "Hybrid approach in the initial aerodynamic, stability and performance calculations of a light airplane", pages = "614-605", number = "4", volume = "20", url = "https://hdl.handle.net/21.15107/rcub_machinery_1796" }
Kostić, I., Stefanović, Z., Petrović, Z., Kostić, O.,& Essari, A.. (2013). Hybrid approach in the initial aerodynamic, stability and performance calculations of a light airplane. in Tehnički vjesnik Faculty of Mechanical Engineering in Slavonski Brod, Faculty of Electrical Engineering in Osijek, Faculty of Civil Engineering in Osijek., 20(4), 605-614. https://hdl.handle.net/21.15107/rcub_machinery_1796
Kostić I, Stefanović Z, Petrović Z, Kostić O, Essari A. Hybrid approach in the initial aerodynamic, stability and performance calculations of a light airplane. in Tehnički vjesnik. 2013;20(4):605-614. https://hdl.handle.net/21.15107/rcub_machinery_1796 .
Kostić, Ivan, Stefanović, Zoran, Petrović, Zlatko, Kostić, Olivera, Essari, Abdulhakim, "Hybrid approach in the initial aerodynamic, stability and performance calculations of a light airplane" in Tehnički vjesnik, 20, no. 4 (2013):605-614, https://hdl.handle.net/21.15107/rcub_machinery_1796 .